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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Collection: Technical Report Archive and Image Library
Aerodynamic characteristics of damping screens

Aerodynamic characteristics of damping screens

Date: January 1, 1950
Creator: Schubauer, G B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic forces on slender plane- and cruciform-wing and body combinations

The aerodynamic forces on slender plane- and cruciform-wing and body combinations

Date: January 1, 1950
Creator: Spreiter, John R
Description: The load distribution, forces, and moments are calculated theoretically for inclined slender wing-body combinations consisting of a slender body of revolution and either a plane or cruciform arrangement of low-aspect-ratio pointed wings. The results are applicable at subsonic and transonic speeds, and at supersonic speeds, provided the entire wing-body combination lies near the center of the Mach cone.
Contributing Partner: UNT Libraries Government Documents Department
American Lignites: Geological Occurrence, Petrographic Composition, And Extractable Waxes

American Lignites: Geological Occurrence, Petrographic Composition, And Extractable Waxes

Date: 1950
Creator: Selvig, W. A.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of spanwise temperature distribution in three types of air-cooled turbine blade

Analysis of spanwise temperature distribution in three types of air-cooled turbine blade

Date: January 1, 1950
Creator: Livingood, John N B
Description: Methods for computing spanwise blade-temperature distributions are derived for air-cooled hollow blades, air-cooled hollow blades with inserts, and air-cooled blades containing internal cooling fins. Individual and combined effects on spanwise blade-temperature distributions of cooling-air and radial heat conduction are determined. In general, the effects of radiation and radial heat conduction were found to be small and the omission of these variations permitted the construction of nondimensional charts for use in determining spanwise temperature distribution through air-cooled turbine blades. An approximate method for determining the allowable stress-limited blade-temperature distribution is included, with brief accounts of a method for determining the maximum allowable effective gas temperatures and the cooling-air requirements. Numerical examples that illustrate the use of the various temperature-distribution equations and of the nondimensional charts are also included.
Contributing Partner: UNT Libraries Government Documents Department
An analysis of supersonic aerodynamic heating with continuous fluid injection

An analysis of supersonic aerodynamic heating with continuous fluid injection

Date: January 1, 1950
Creator: Klunker, E G
Description: An analysis of the steady-state aerodynamic heating problem at high-supersonic speeds is made for two-dimensional flows with laminar boundary layers. The aerodynamic heating is shown to be reduced substantially by injecting a small amount of coolant through a porous surface into the boundary layer. The analysis includes calculations of the cooling requirements and equilibrium surface temperatures for flat plates and for an equilibrium surface temperatures for flat plates and for flat porous surfaces with several rates of fluid injection at Mach numbers from 5 to 15 and altitudes from sea level to 200,000 feet. Some calculations of the skin friction are also included.
Contributing Partner: UNT Libraries Government Documents Department
Annual report of the National Advisory Committee for Aeronautics (33rd).administrative report including Technical Report nos. 863 to 891

Annual report of the National Advisory Committee for Aeronautics (33rd).administrative report including Technical Report nos. 863 to 891

Date: January 1, 1950
Creator: unknown
Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Contributing Partner: UNT Libraries Government Documents Department
The application of Green's theorem to the solution of boundary-value problems in linearized supersonic wing theory

The application of Green's theorem to the solution of boundary-value problems in linearized supersonic wing theory

Date: January 1, 1950
Creator: Heaslet, Max A
Description: Following the introduction of the linearized partial differential equation for nonsteady three-dimensional compressible flow, general methods of solution are given for the two and three-dimensional steady-state and two-dimensional unsteady-state equations. It is also pointed out that, in the absence of thickness effects, linear theory yields solutions consistent with the assumptions made when applied to lifting-surface problems for swept-back plan forms at sonic speeds. The solutions of the particular equations are determined in all cases by means of Green's theorem, and thus depend on the use of Green's equivalent layer of sources, sinks, and doublets. Improper integrals in the supersonic theory are treated by means of Hadamard's "finite part" technique.
Contributing Partner: UNT Libraries Government Documents Department
Application of radial-equilibrium condition to axial-flow compressor and turbine design

Application of radial-equilibrium condition to axial-flow compressor and turbine design

Date: January 1, 1950
Creator: Wu, Chung-Hua
Description: Basic general equations governing the three-dimensional compressible flow of gas through a compressor or turbine are given in terms of total enthalpy, entropy, and velocity components of the gas. Two methods of solution are obtained for the simplified, steady axially symmetric flow; one involves the use of a number of successive planes normal to the axis of the machine and short distances apart, and the other involves only three stations for a stage in which an appropriate radial-flow path is used. Methods of calculation for the limiting cases of zero and infinite blade aspect ratios and an approximate method of calculation for finite blade aspect ratio are also given. In these methods, the blade loading and the shape of the annular passage wall may be arbitrarily specified.
Contributing Partner: UNT Libraries Government Documents Department
Application of the Laplace transformation to the solution of the lateral and longitudinal stability equations

Application of the Laplace transformation to the solution of the lateral and longitudinal stability equations

Date: January 1, 1950
Creator: Mokrzycki, G A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The application of the statistical theory of extreme values to gust-load problems

The application of the statistical theory of extreme values to gust-load problems

Date: January 1, 1950
Creator: Press, Harry
Description: An analysis is presented which indicates that the statistical theory of extreme values is applicable to the problems of predicting the frequency of encountering the larger gust loads and gust velocities for both specific test conditions as well as commercial transport operations. The extreme-value theory provides an analytic form for the distributions of maximum values of gust load and velocity. Methods of fitting the distribution are given along with a method of estimating the reliability of the predictions. The theory of extreme values is applied to available load data from commercial transport operations. The results indicate that the estimates of the frequency of encountering the larger loads are more consistent with the data and more reliable than those obtained in previous analyses. (author).
Contributing Partner: UNT Libraries Government Documents Department
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